A new approach to mathematical simulation of motion of space vehicles with high-thrust rocket engines is proposed. It bases on the sequential contraction of the admissible control set by using of the necessary optimality conditions. The mathematical models of bipropellant rocket engines obtained with this approach are discussed. The main idea of the proposed approach is to decrease the complexity of mathematical description of the controllable object. This may be done with the use of the consequent reducing of the admissible positions in the control space using the Rodhen's approach: to throw off the admissible control subsets which do not comply with optimality condition (similar to Rodhen's elimination of redundant part of a rock when creating his sculptures). The adequacy simplicity balance of proposed models of spacecraft equipped with the liquid rocket engine is suitable for analyze and solution of appropriate optimal control problems using well-known approach (Chernous'ko,1975).
Complexity-adequacy dilemma for mathematical simulation of spacecraft motion
Kompliziertheit-Angemessenheit-Dilemma für die mathematische Simulation der Raumfahrzeugbewegung
2004
6 Seiten
Aufsatz (Konferenz)
Datenträger
Englisch
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